直升机中减飞溅润滑流场分析与优化方法

Analysis and optimization method for flow field of intermediate gearbox splash lubrication in helicopters

为探究某型直升机中间减速器飞溅润滑油-气两相流分布与参数优化方法,首先基于计算流体力学(CFD)思想建立了中减飞溅润滑数值计算模型;采用多相流(VOF)及动网格等模型计算获得了机匣内部的油液分布与导油管的润滑油流量;分析了浸油深度和输入转速对齿面与轴承(通过导油管的润滑油流量体现)润滑效果的影响规律。然后在直升机中减传动试验台上开展试验,验证仿真的可行性。结果显示:建议的中减浸油深度为17~26mm、输入转速为4000~6000r/min;试验测得4个导油管的润滑油流量趋势与CFD仿真计算结果一致,且有一个导油管收集不到润滑油,说明该导油管的结构不合理。

To explore the distribution and parameter optimization method for the oil-air two-phase flow field of the intermediate gearbox under splash lubrication,a numerical model of the intermediate gearbox under splash lubrication was established based on Computational Fluid Dynamics(CFD)firstly.The Volume of Fluid(VOF)multiphase flow model and dynamic mesh model were used to calculate the oil distribution in the gearbox and the oil flow rate of the oil guide tube.The influences of the oil immersion depth and rotational speed on the lubrication effect of the gear face and bearing(reflected by the oil flow rate of the oil guide tube)were analyzed.Furthermore,an experiment was conducted on the intermediate gearbox transmission test-rig to verify the feasibility of the simulation.Results show that it is recommended that the oil immersion depth and rotational speed are in the ranges of 17-26 mm and 4000-6000 r/min,respectively.The flow trend of the oil in the four oil guide tubes was consistent with the CFD simulation results,while no oil was collected in one oil guide tube,showing the unreasonableness of the structure of this oil guide tube.